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Satellite attitude control method for ground point staring imaging

A satellite attitude control and gaze imaging technology, applied in attitude control and other directions, can solve the problems of complex algorithms, verified, and satellite gaze attitude control methods remain at the theoretical level, etc.

Active Publication Date: 2015-12-02
NAT UNIV OF DEFENSE TECH
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  • Description
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Problems solved by technology

Most of the researches on satellite gaze attitude control methods in the existing literature remain at the theoretical level, the algorithms are relatively complex, and have not been verified in actual engineering

Method used

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  • Satellite attitude control method for ground point staring imaging
  • Satellite attitude control method for ground point staring imaging
  • Satellite attitude control method for ground point staring imaging

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Embodiment Construction

[0078] The present invention will be further described in detail below in conjunction with specific embodiments and accompanying drawings.

[0079] A satellite attitude control method for ground point staring imaging, the specific steps are as follows:

[0080] Step 1: Given satellite orbit state X S =[R S ,V S ] and the ground point space coordinate R T

[0081] R S =[1590360.821,6167656.906,2550832.279] T (m)

[0082] V S =[1712.222,2465.737,-7003.521] T (m / s)

[0083] R T =[1660202.218,5739273.073,2225233.992] T (m)

[0084] Among them, R S is the satellite’s geocentric inertial frame position, V S is the speed of the satellite’s earth-inertial frame, R T is the position in the geocentric inertial frame of the ground point.

[0085] Step 2: Calculate the error between the actual angular velocity and the expected angular velocity

[0086] 1) Calculate the staring Euler angle

[0087] Calculate the normal unit vector of the satellite's orbital plane at the c...

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Abstract

For the problem of staring from a satellite to a ground point, the invention provides a satellite attitude control method for ground point staring imaging. The method includes the steps: calculating an expected staring Euler angle and an expected angular velocity on the basis of a given satellite track state and a given ground point space coordinate, calculating the margin of error between an actual angular velocity and the expected angular velocity, then calculating the value of deviation between an optical axis and a ground point direction on the basis of an actual attitude, selecting a control law parameter, and finally calculating the controlled variable of the moment of a flywheel. In terms of applications, the attitude angle and the angular velocity of a satellite are measured and obtained by an attitude determination system. The controlled variable calculated by the method is transmitted to an executing mechanism, and then a ground point staring attitude control function is achieved. According to the method, a yaw angle can keep being zero, so an image will not rotate within the field of view of a camera, and the image is convenient to observe and analyze. The algorithm of the method is simple, the computation is easy, and the method is easy to achieve in terms of engineering. Moreover, the method exhibits high directional control precision and good directional stability.

Description

technical field [0001] The invention relates to a satellite attitude control method in the aerospace field, which provides an attitude control method for a satellite to stare at a ground point, and belongs to the technical field of automatic control. Background technique [0002] Satellite miniaturization is one of the trends in the development of low-earth orbit satellites. Due to the reduction in volume and mass, it has the advantages of agile attitude maneuvering, low energy consumption, and low cost. It can be widely used in reconnaissance and surveillance, earth observation, environmental monitoring, and emergency response. Disaster relief, scientific exploration and other fields have important application value and broad application prospects. [0003] Staring imaging refers to the rapid attitude maneuvering of the satellite so that the optical axis of the camera fixed on the star always points to the desired ground point, so that the ground scene can be observed and r...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 连一君曾国强项军华吴国福税海涛韩大鹏李志军袁福高玉东
Owner NAT UNIV OF DEFENSE TECH
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